A method and apparatus for life assessment of a turbine disk-baffle assembly

Abstract

The application relates to the technical field of aero-engines and discloses a life evaluation method and device for a turbine disc-baffle assembly, which comprises the following steps: stress analysis and simplification are carried out on an original model of the turbine disc-baffle assembly to obtain a simplified model; the number of feature parts in the simplified model is adjusted to establish a cyclically symmetric model; equivalent conversion is carried out on the cyclically symmetric model to obtain an equivalent model; contact stress analysis is carried out on the basis of the matching state between the turbine disc and the baffle in the equivalent model to screen a target matching state; a transient full load is obtained; stress analysis is carried out on the equivalent model in combination with the target matching state to extract stress amplitude; and fatigue life is evaluated on the basis of the stress amplitude. The application simulates the radial and axial contact matching relationship of the turbine disc and the baffle, simultaneously considers the finite element model scale to improve the calculation efficiency and precision, improves the stress calculation accuracy, and simultaneously carries out accurate stress analysis and life design on the basis of the transient load history and matching gap dispersity.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically to a method and apparatus for assessing the lifespan of a turbine disk-baffle assembly. Background Technology

[0002] As critical and life-limited components of aero-engines, gas turbine disks and baffles operate under extreme environments of high temperature, high speed, and high aerodynamic loads for extended periods, enduring cyclic loads. They are prone to failure due to low-cycle fatigue, leading to adverse effects that are often catastrophic. Therefore, conducting low-cycle fatigue life assessments of turbine disk-baffle assemblies is a necessary prerequisite for ensuring their safe and reliable operation throughout their entire life cycle.

[0003] Currently, existing technologies primarily employ two-dimensional planar models and fully three-dimensional overall models for modeling, using steady-state design points for life assessment, with the steady-state maximum stress as the core input parameter for low-cycle fatigue life analysis. However, during actual service, engines frequently undergo state transitions such as starting, acceleration, cruising, and deceleration, resulting in dynamic changes in component loads. Existing technologies do not consider the differences in stress response during these multi-condition transitions, leading to inaccurate stress calculations and significant deviations between life assessment results and actual conditions. This increases operational risks and reduces engine reliability and safety.

[0004] Furthermore, in terms of modeling methods, two-dimensional planar models perform two-dimensional equivalent treatment on parts such as tenons and grooves, which significantly affects radial contact forces and involves data transfer between two-dimensional and three-dimensional models, resulting in low computational efficiency. Although the full three-dimensional overall model has high geometric accuracy, the model size is huge, and coupled with strong contact nonlinearity, the computational efficiency is low and it may even be difficult to converge. Summary of the Invention

[0005] This invention provides a method and apparatus for assessing the lifespan of a turbine disk-baffle assembly, thereby addressing one of the technical problems existing in the prior art.

[0006] In a first aspect, the present invention provides a method for assessing the lifespan of a turbine disk-baffle assembly, the method comprising: The original model of the turbine disk-baffle assembly was subjected to stress analysis and simplified to obtain a simplified model; Adjust the number of feature parts in the simplified model to establish a cyclic symmetric model; By performing an equivalent transformation on the cyclic symmetric model, an equivalent model with mechanical behavior equivalent to the original model is obtained; Contact stress analysis is performed based on the fit between the turbine disk and the baffle in the equivalent model to screen the target fit state; Obtain the transient full load of the turbine disk-baffle assembly, and perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude; The fatigue life of the turbine disk-baffle assembly is assessed based on stress amplitude.

[0007] This invention simplifies the original model through stress analysis and then adjusts the number of feature parts to establish a cyclic symmetric model, effectively reducing the model size and improving computational efficiency and accuracy. By performing equivalent conversion on the cyclic symmetric model, its mechanical behavior is made essentially equivalent to the original model, ensuring the accuracy of subsequent stress analysis. By applying various mating states to the equivalent model for contact stress analysis, the radial and axial contact mating relationships between the turbine disk and the baffle can be fully simulated, allowing for the selection of the target mating state. Furthermore, by considering the actual load changes under transient time histories and combining this with the target mating state, stress analysis is accurately performed and stress amplitudes are extracted. Fatigue life is then assessed based on these stress amplitudes, improving the accuracy of life assessment, enhancing engine reliability and safety, and providing a basis for lightweight design and high reliability assurance of key aero-engine components.

[0008] In one alternative implementation, the original model of the turbine disk-baffle assembly is subjected to stress analysis and simplified to obtain a simplified model, including: Obtain the initial full load of the turbine disk-baffle assembly in a typical flight mission; Stress analysis was performed on the original model based on the initial full load to obtain the stress at multiple characteristic parts of the turbine disk-baffle assembly; For each feature region, the number of the first cycle corresponding to the stress at the feature region is determined based on the material fatigue performance data. Based on the first iteration count of each feature region, multiple feature regions are divided into critical regions and non-critical regions; The non-critical parts are simplified in the original model to obtain the simplified model.

[0009] This invention provides load input for subsequent stress analysis by obtaining an initial full load. Based on this initial full load, stress analysis is performed to obtain the stress levels of each characteristic location. The first cycle count of each characteristic location is obtained from material fatigue performance data, quantifying its lifespan performance. By comparing the cycle counts of each location, key locations that play a dominant role in component lifespan are identified, allowing subsequent analysis to focus on weak points. While maintaining the accuracy of key locations, non-key locations are simplified, effectively reducing model complexity, model size, and computation time.

[0010] In one alternative implementation, the number of feature parts in the simplified model is adjusted to establish a cyclic symmetric model, including: The range of the cyclic symmetric model is determined based on the number of bolt holes in the simplified model; Adjust the number of tenons in the simplified model so that the number of tenons and the number of bolt holes are in a multiple relationship; Based on the range of the cyclic symmetric model, cyclic symmetric boundary conditions are applied to the simplified model after adjusting the number of parameters to obtain the cyclic symmetric model.

[0011] This invention determines the range of the cyclic symmetry model based on the number of bolt holes, providing a geometric boundary basis for subsequent modeling. Then, the number of tenons is adjusted to be an integer multiple of the number of bolt holes, ensuring the structure meets the geometric conditions of cyclic symmetry. This allows the application of cyclic symmetry boundary conditions, enabling the mechanical response of the entire model to be obtained by performing finite element calculations on only one sector, further reducing the model size and improving computational efficiency.

[0012] In one optional implementation, an equivalent transformation is performed on the cyclic symmetric model to obtain an equivalent model whose mechanical behavior is equivalent to that of the original model, including: Calculate the equivalent material density at the rim and the equivalent centrifugal load applied at the tenon tooth surface of the rim tenon groove; Based on the difference in radial deformation before and after the adjustment, the elastic modulus of the material at the equivalent rear rim is calculated; Based on the equivalent material density at the rim, the equivalent centrifugal load applied to the tenon tooth surface of the rim groove, and the elastic modulus of the material at the rim, the corresponding parameters of the cyclic symmetric model are updated to obtain the equivalent model.

[0013] This invention achieves equivalent conversion of density, load, and stiffness, making the cyclic symmetric model with adjusted tenon and slot numbers essentially equivalent to the original model in terms of centrifugal load, blade force transmission, and rim support stiffness. This significantly reduces the model size while ensuring the accuracy of mechanical behavior calculations, providing an accurate and efficient model foundation for subsequent transient stress analysis and life assessment.

[0014] In one alternative implementation, the material density at the equivalent rear rim is calculated using the following formula:

[0015] In the formula, This represents the material density at the equivalent rear rim. This represents the material density at the rim in the original model; This represents the volume of a single tenon in the original model; This represents the volume of a single tenon in a cyclically symmetric model. Represents the centroid radius of a single tenon in the original model; Represents the centroid radius of a single tenon in a cyclic symmetric model; This indicates the number of tenons and mortises in the original model; This indicates the number of tenons and slots in a cyclically symmetric model; The equivalent centrifugal load applied to the tenon tooth surface of the wheel rim tenon groove is calculated using the following formula:

[0016] In the formula, This represents the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent effect. This represents the centrifugal load applied to the tenon tooth surface of the rim groove in the original model.

[0017] This invention performs equivalent conversions of density and centrifugal load by adjusting the number of tenons and slots before and after the adjustment, so that the adjusted cyclic symmetric model is consistent with the original model in terms of rim centrifugal load and blade force transmission, thus ensuring the accuracy of subsequent stress analysis and life assessment.

[0018] In one optional implementation, the elastic modulus of the material at the equivalent rear rim is calculated based on the difference in radial deformation before and after adjustment, including: Based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon tooth surface of the rim tenon, the first finite element model of the turbine disk is established. Based on the number of tenons in the cyclic symmetric model, the material density at the equivalent wheel rim, and the centrifugal load applied at the tenon tooth surface of the wheel rim tenon after the equivalent process, a second finite element model of the turbine disk is established. The elastic modulus of the material at the rim of the original model is input into the first finite element model and the second finite element model respectively, and finite element calculation is performed to obtain the first average radial deformation and the second average radial deformation. Calculate the ratio of the second average radial deformation to the first average radial deformation, and multiply the ratio by the elastic modulus of the material at the rim of the original model to determine the elastic modulus of the material at the equivalent rim.

[0019] This invention establishes finite element models before and after adjustment, calculates radial deformation using the original modulus, and infers the equivalent modulus based on the deformation difference. This ensures that the adjusted model maintains consistency with the original model in terms of flange support stiffness, thereby simplifying the model while ensuring the accuracy of turbine disk-baffle contact force calculation, and guaranteeing the accuracy of subsequent stress analysis and life assessment.

[0020] In one optional implementation, contact stress analysis is performed based on the fit between the turbine disk and the baffle in the equivalent model to screen target fit states, including: Establish the contact pair between the turbine disk and the baffle in the equivalent model; Based on the design tolerances of the turbine disk and the baffle, various mating states between the turbine disk and the baffle are determined. Contact stress is calculated on the equivalent model based on each mating state to obtain the contact stress of key parts; The fit state corresponding to the maximum contact stress is determined as the target fit state.

[0021] This invention establishes a contact pair between the turbine disk and the baffle, providing a prerequisite for subsequent contact stress analysis. Then, based on design tolerances, multiple fit states are determined. Each fit state is input into an equivalent model for contact stress calculation, obtaining the contact stress of key components under different fit states. The impact of fit state changes on key components is quantified, thereby selecting the fit state that maximizes the contact stress of key components as the target fit state. This ensures that subsequent life assessments cover the most unfavorable assembly conditions, avoiding deviations from reality due to the failure to consider extreme fit states.

[0022] In one optional implementation, the transient full load of the turbine disk-baffle assembly is obtained, and stress analysis is performed on the equivalent model in conjunction with the target fit state to extract the stress amplitude, including: Obtain the transient full load, and based on the transient full load and the target fit state, perform stress analysis on the equivalent model to extract the peak stress and valley stress of each key part; Half the difference between the peak stress and the valley stress is taken as the stress amplitude of the critical part.

[0023] This invention introduces transient full load to replace the traditional steady-state design point load, and combines the target fit state to perform transient contact finite element stress analysis. This allows the peak and valley stresses of each key component in real flight mission cycles to be obtained, and the stress amplitude to be calculated. This provides more accurate stress input parameters for subsequent low-cycle fatigue life assessment.

[0024] In one alternative implementation, assessing the fatigue life of the turbine disk-baffle assembly based on stress amplitude includes: For each critical component, based on material fatigue performance data, the number of second cycles corresponding to the stress amplitude of the critical component is determined; Calculate the ratio of the second cycle number to the preset lifetime dispersion coefficient, and use it as the third cycle number for critical parts; The minimum number of the third cycle counts for all critical components is taken as the fatigue life of the turbine disk-baffle assembly.

[0025] This invention substitutes the stress amplitude of each critical component into the material fatigue performance data to obtain the corresponding second cycle number. Then, it divides this value by the life dispersion coefficient to obtain the third cycle number. The minimum value of the third cycle number among all critical components is taken as the fatigue life of the component. While considering the dispersion of material data and the uncertainty of calculation, this invention ensures that the evaluation results cover the weakest link in the component, providing a reliable basis for the life design and safety assessment of turbine disk-baffle components.

[0026] In a second aspect, the present invention provides a life assessment device for a turbine disk-baffle assembly, the device comprising: The simplification module is used to perform stress analysis and simplify the original model of the turbine disk-baffle assembly to obtain a simplified model; The adjustment module is used to adjust the number of feature parts in the simplified model and establish a cyclic symmetric model; The equivalent conversion module is used to perform equivalent conversion on the cyclic symmetric model to obtain an equivalent model whose mechanical behavior is equivalent to that of the original model. The first analysis module is used to perform contact stress analysis based on the fit state between the turbine disk and the baffle in the equivalent model, and to screen the target fit state. The second analysis module is used to obtain the transient full load of the turbine disk-baffle assembly, and to perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude; An evaluation module is used to assess the fatigue life of the turbine disk-baffle assembly based on stress amplitude.

[0027] Thirdly, the present invention provides an electronic device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the computer instructions to perform the life assessment method for the turbine disk-baffle assembly described in the first aspect or any corresponding embodiment thereof.

[0028] Fourthly, the present invention provides a computer-readable storage medium storing computer instructions for causing a computer to perform the life assessment method for a turbine disk-baffle assembly according to the first aspect or any corresponding embodiment thereof. Attached Figure Description

[0029] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 2(a) is a schematic diagram of a two-dimensional planar geometric model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 2(b) is a schematic diagram of a two-dimensional axisymmetric finite element mesh model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 3(a) is a schematic diagram of a three-dimensional full-circle geometric model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 3(b) is a schematic diagram of a three-dimensional full-circle finite element mesh model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 4 This is a flowchart of a life assessment method for a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 5(a) is a schematic diagram of a three-dimensional cyclic symmetric geometric model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 5(b) is a schematic diagram of a three-dimensional cyclic symmetric finite element mesh model of a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 6 This is a schematic diagram of stress curves according to an embodiment of the present invention; Figure 7 This is a structural block diagram of a life assessment device for a turbine disk-baffle assembly according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the hardware structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] It is understood that before using the technical solutions disclosed in the various embodiments of the present invention, users should be informed of the types, scope of use, and usage scenarios of the personal information involved in the present invention and their authorization should be obtained in accordance with relevant laws and regulations through appropriate means.

[0033] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0034] Figure 1 This is a schematic diagram of a turbine disk-baffle assembly according to an embodiment of the present invention, as shown below. Figure 1 As shown, the turbine disk-baffle assembly is a critical and life-limited component of an aero-engine; failure due to low-cycle fatigue can lead to catastrophic consequences. Therefore, conducting low-cycle fatigue life assessment of the turbine disk-baffle assembly is a necessary prerequisite for ensuring its safe and reliable operation throughout its entire life cycle.

[0035] Currently, two-dimensional planar models and full three-dimensional global models are mainly used for modeling, and life assessment is performed through steady-state design points, that is, the steady-state maximum stress is used as the core input parameter for low-cycle fatigue life analysis. The two-dimensional planar model includes the two-dimensional planar geometric model shown in Figure 2(a) and the two-dimensional axisymmetric finite element mesh model shown in Figure 2(b); the full three-dimensional global model includes the three-dimensional full-circle geometric model shown in Figure 3(a) and the three-dimensional full-circle finite element mesh model shown in Figure 3(b). However, the two-dimensional planar model performs two-dimensional equivalent treatment on parts such as tenons and grooves, which significantly affects the radial contact force, and involves data transfer between the two-dimensional and three-dimensional models, resulting in low computational efficiency. Although the full three-dimensional global model has high geometric accuracy, its large model size, coupled with strong contact nonlinearity, leads to low computational efficiency and even difficulty in convergence.

[0036] Furthermore, during actual service, engines frequently undergo state transitions such as starting, acceleration, cruising, and deceleration, resulting in dynamic changes in component loads. The aforementioned method does not consider the differences in stress response during these multi-condition transitions, leading to inaccurate stress calculations and significant deviations between life assessment results and actual conditions. This, in turn, increases operational risks and reduces engine reliability and safety.

[0037] According to an embodiment of the present invention, a method for life assessment of a turbine disk-baffle assembly is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0038] This embodiment provides a method for assessing the lifespan of a turbine disk-baffle assembly. Figure 4 This is a flowchart of a life assessment method for a turbine disk-baffle assembly according to an embodiment of the present invention, such as... Figure 4 As shown, the process includes the following steps: Step S401: Perform stress analysis on the original model of the turbine disk-baffle assembly and simplify it to obtain a simplified model.

[0039] Specifically, performing finite element stress analysis on the original model of the turbine disk-baffle assembly simplifies the parts that have a smaller impact on the lifespan of the turbine disk or baffle, effectively reducing the model size and improving computational efficiency and accuracy.

[0040] Step S402: Adjust the number of feature parts in the simplified model and establish a cyclic symmetric model.

[0041] Specifically, by adjusting the number of feature parts in the simplified model, a cyclically symmetric model is established, ensuring that the model's geometry, material properties, loads, and constraints completely coincide after rotating it at equal angles along a central axis. Furthermore, establishing a cyclically symmetric model based on the simplified model can further reduce the model size and improve computational efficiency and accuracy.

[0042] Step S403: Perform an equivalent conversion on the cyclic symmetric model to obtain an equivalent model whose mechanical behavior is equivalent to that of the original model.

[0043] Specifically, since the cyclic symmetric model is obtained by adjusting the number of feature parts, the mechanical behavior of the model will deviate from the original model. If the parameters of the original model are directly used, the stress analysis will be distorted. Therefore, it is necessary to perform adaptive equivalent calculations on the cyclic symmetric model to obtain an equivalent model that is basically the same as the original model, so as to ensure the accuracy of subsequent stress analysis and life assessment.

[0044] Step S404: Based on the fit between the turbine disk and the baffle in the equivalent model, perform contact stress analysis and select the target fit state.

[0045] Specifically, such as Figure 1 As shown, there are radial and axial contacts between the turbine disk and the baffle. Due to the critical dimensional design tolerances of the turbine disk and the baffle at the radial and axial mating positions, there are multiple possibilities for the actual mating state between them, and the contact stress varies significantly under different mating states. By applying multiple mating states to the equivalent model for contact stress analysis, the radial and axial contact mating relationship between the turbine disk and the baffle can be fully simulated, thereby selecting the target mating state for subsequent transient stress analysis and life assessment.

[0046] Step S405: Obtain the transient full load of the turbine disk-baffle assembly, and perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude.

[0047] Specifically, based on typical engine flight missions (such as a complete cycle consisting of start-up, acceleration, cruise, and deceleration), the transient full loads of the turbine disk-baffle assembly, including rotational speed, temperature load, and aerodynamic load, are obtained under the consideration of transient time history. Combined with the target coordination state, these are used as the input conditions for the finite element simulation calculation of the equivalent model, and the stress amplitude is extracted from the calculated stress results.

[0048] Step S406: Evaluate the fatigue life of the turbine disk-baffle assembly based on the stress amplitude.

[0049] Specifically, by considering the actual load changes under transient time history, the accuracy of life assessment can be effectively improved, providing a basis for the lightweight design and high reliability assurance of key components of aero-engines.

[0050] This invention simplifies the original model through stress analysis and then adjusts the number of feature parts to establish a cyclic symmetric model, effectively reducing the model size and improving computational efficiency and accuracy. By performing equivalent conversion on the cyclic symmetric model, its mechanical behavior is made essentially equivalent to the original model, ensuring the accuracy of subsequent stress analysis. By applying various mating states to the equivalent model for contact stress analysis, the radial and axial contact mating relationships between the turbine disk and the baffle can be fully simulated, allowing for the selection of the target mating state. Furthermore, by considering the actual load changes under transient time histories and combining this with the target mating state, stress analysis is accurately performed and stress amplitudes are extracted. Fatigue life is then assessed based on these stress amplitudes, improving the accuracy of life assessment, enhancing engine reliability and safety, and providing a basis for lightweight design and high reliability assurance of key aero-engine components.

[0051] This embodiment provides a method for assessing the lifespan of a turbine disk-baffle assembly, which specifically includes the following steps: Step S501: Perform stress analysis on the original model of the turbine disk-baffle assembly and simplify it to obtain a simplified model.

[0052] Specifically, step S501 includes: Step S5011: Obtain the initial full load of the turbine disk-baffle assembly in a typical flight mission.

[0053] Specifically, based on the typical flight mission of an aircraft or helicopter, the initial full loads such as rotational speed, temperature, aerodynamic load, and axial preload that the turbine disk and baffle bear at typical steady-state design points (such as maximum speed, maximum temperature, etc.) are obtained.

[0054] Step S5012: Perform stress analysis on the original model based on the initial full load to obtain the stress of multiple characteristic parts of the turbine disk-baffle assembly.

[0055] Specifically, the initial full load is applied to the original model of the turbine disk-baffle assembly, and the stress of each feature part (such as tenon, bolt hole, wheel center, baffle stop, venting groove, etc.) is calculated through finite element stress analysis.

[0056] Step S5013: For each feature part, based on the material fatigue performance data, determine the first cycle number corresponding to the stress of the feature part.

[0057] Specifically, the material fatigue performance data are SN curves or ε-N curves, which describe the relationship between stress or strain and fatigue life of the turbine disk-baffle assembly material under cyclic loading. By substituting the stress at each characteristic location into the corresponding curve, the number of cycles corresponding to each characteristic location under that stress can be obtained.

[0058] Step S5014: Based on the first loop count of each feature region, divide the multiple feature regions into critical regions and non-critical regions.

[0059] Specifically, the number of first cycles for each characteristic part is compared. The lower the number of first cycles, the more likely the characteristic part is to develop fatigue cracks under cyclic loading, which has a greater impact on the life of the turbine disk or baffle. Therefore, it is identified as a critical part. Other characteristic parts (such as end teeth, counterweight holes, etc.) are classified as non-critical parts.

[0060] Step S5015: Simplify the non-critical parts in the original model to obtain the simplified model.

[0061] Specifically, the true geometric features of key parts are preserved in the original model, while non-key parts are filled or cut off. This effectively reduces the model size while ensuring the accuracy of stress calculation in key parts, thereby improving the efficiency and accuracy of subsequent calculations.

[0062] Step S502: Adjust the number of feature parts in the simplified model and establish a cyclic symmetric model.

[0063] Specifically, step S502 includes: Step S5021: Determine the range of the cyclic symmetric model based on the number of bolt holes in the simplified model.

[0064] Specifically, the minimum periodic sector that can be selected for the cyclic symmetric model is determined based on the number of bolt holes. For example, if there are 8 bolt holes, a 1 / 8 model containing 1 bolt hole or a 1 / 4 model containing 2 bolt holes can be selected. The specific range is reasonably selected based on the model size and computing resources to ensure the feasibility and computational efficiency of subsequent cyclic symmetric modeling.

[0065] Step S5022: Adjust the number of tenons in the simplified model so that the number of tenons and the number of bolt holes are in a multiple relationship.

[0066] Specifically, without changing the tenon and mortise configuration, the number of tenons and mortises is adjusted to be a multiple of the number of bolt holes, thus ensuring that the adjusted model meets the cyclic symmetry condition. For example, if there are 8 bolt holes and 45 tenons and mortises, the number of tenons and mortises is adjusted to 40 or 48.

[0067] Step S5023: Based on the range of the cyclic symmetric model, apply cyclic symmetric boundary conditions to the simplified model after adjusting the number of parameters to obtain the cyclic symmetric model.

[0068] Specifically, in the simplified model after adjusting the number of tenons and slots, based on the range of the cyclic symmetric model determined in step S5021 (such as 1 / 8 or 1 / 4 sector), cyclic symmetric boundary conditions are applied to the sector cutting surface to ensure the continuity and periodicity requirements of the model after circumferential rotation, thereby establishing a cyclic symmetric model, as shown in Figure 5(a) as a three-dimensional cyclic symmetric geometric model and Figure 5(b) as a three-dimensional cyclic symmetric finite element mesh model. This model only requires finite element calculation of one sector to obtain the mechanical response of the entire circumference model, effectively reducing the model size and calculation time while ensuring calculation accuracy.

[0069] Step S503: Perform an equivalent conversion on the cyclic symmetric model to obtain an equivalent model whose mechanical behavior is equivalent to that of the original model.

[0070] Specifically, step S503 includes: Step S5031: Calculate the material density at the equivalent wheel rim and the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent calculation.

[0071] Specifically, after adjusting the number of tenons, both the material density at the rim and the centrifugal load on the tenon surface will deviate from their original values. If the original parameters are used directly, the centrifugal load will be distorted. Therefore, an adaptive equivalent calculation is required for both. Since the rim radius remains unchanged but the number of tenons changes, the volume of the tenon portion of the remaining material at the rim changes, and the centroid radius changes slightly. For the material density at the rim, the total centrifugal load generated at the rim must be kept equal before and after the adjustment. That is, the equivalent material density at the rim is obtained by performing an equivalent calculation using the following formula (1): (1) In the formula, This represents the material density at the equivalent rear rim. This represents the material density at the rim in the original model; This represents the volume of a single tenon in the original model; This represents the volume of a single tenon in a cyclically symmetric model. Represents the centroid radius of a single tenon in the original model; Represents the centroid radius of a single tenon in a cyclic symmetric model; This indicates the number of tenons and mortises in the original model; This indicates the number of tenons and slots in a cyclically symmetric model.

[0072] For the centrifugal load applied to the tenon tooth surface of the wheel rim groove, the total centrifugal load generated by the turbine rotor blades or counterweight blades before and after adjustment must be equivalent. That is, the equivalent centrifugal load applied to the tenon tooth surface of the wheel rim groove is obtained by equivalent calculation using the following formula (2): (2) In the formula, This represents the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent effect. This represents the centrifugal load applied to the tenon tooth surface of the rim groove in the original model.

[0073] Step S5032: Based on the difference in radial deformation of the model before and after adjustment, calculate the elastic modulus of the material at the equivalent rear rim.

[0074] In some optional implementations, step S5032 above includes: Step a1: Based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon teeth at the rim tenon, establish the first finite element model of the turbine disk.

[0075] Specifically, after adjusting the number of tenons, in order to ensure that the support stiffness of the turbine disk rim to the baffle is basically equivalent to the original structural stiffness, it is necessary to perform adaptive equivalent calculations on the elastic modulus and other properties of the material at the turbine disk rim. First, based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon teeth of the rim tenons, a first finite element model of the turbine disk is established as the benchmark model for stiffness equivalence.

[0076] Step a2: Based on the number of tenons in the cyclic symmetric model, the material density at the equivalent wheel rim, and the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent process, a second finite element model of the turbine disk is established.

[0077] Specifically, based on the number of tenons in the adjusted cyclic symmetric model, the equivalent material density at the rim obtained from the above steps, and the equivalent centrifugal load applied to the tenon tooth surface of the rim tenon, a second finite element model of the turbine disk is established.

[0078] Step a3: Input the elastic modulus of the material at the rim of the original model into the first finite element model and the second finite element model respectively, perform finite element calculations, and obtain the first average radial deformation and the second average radial deformation.

[0079] Specifically, the elastic modulus of the material at the rim of the original model is input into the first finite element model and the second finite element model respectively. Finite element calculations are performed under the same steady-state design point rotational speed and temperature load to obtain the first average radial deformation at the radial cylindrical surface stop of the rim of the first finite element model and the second average radial deformation at the same location of the second finite element model.

[0080] Step a4: Calculate the ratio of the second average radial deformation to the first average radial deformation, and multiply the ratio by the elastic modulus of the material at the rim of the original model to determine the elastic modulus of the material at the equivalent rim.

[0081] Specifically, the ratio of the second average radial deformation to the first average radial deformation is calculated, and this ratio is multiplied by the elastic modulus of the material at the rim of the original model. The product is the elastic modulus of the material at the rim after the adjustment, so that the average radial deformation of the adjusted model at the radial cylindrical surface stop of the rim is consistent with that of the original model, thereby ensuring that the support stiffness of the rim to the baffle after adjusting the number of tenons is basically the same as that of the original model.

[0082] Step S5033: Based on the material density at the equivalent rear rim, the centrifugal load applied to the tenon tooth surface of the equivalent rear rim, and the elastic modulus of the material at the equivalent rear rim, update the corresponding parameters of the cyclic symmetric model to obtain the equivalent model.

[0083] Specifically, in the cyclic symmetric model, the material density at the rim, the centrifugal load applied to the tenon tooth surface of the rim groove, and the elastic modulus of the material at the rim are updated to the equivalent values ​​calculated in the above steps. This makes the updated model basically equivalent to the original model in terms of centrifugal load, blade force transmission, and rim support stiffness, completing the closed loop from geometric adjustment to mechanical equivalence, and obtaining an equivalent model that can be used for subsequent stress analysis and life assessment.

[0084] Step S504: Based on the fit between the turbine disk and the baffle in the equivalent model, perform contact stress analysis and select the target fit state.

[0085] Specifically, step S504 includes: Step S5041: Establish the contact pair between the turbine disk and the baffle in the equivalent model.

[0086] Specifically, in the equivalent model, based on the actual assembly relationship between the turbine disk and the baffle, contact pairs are established at the radial cylindrical positioning surface and the axial bolt connection surface to simulate the contact force transmission and constraint relationship between the two, providing a modeling basis for subsequent contact stress analysis considering changes in the fit state.

[0087] Step S5042: Based on the design tolerances of the turbine disk and the baffle, determine the various mating states between the turbine disk and the baffle.

[0088] Specifically, the turbine disk and baffle are assembled into a component through radial and axial mating surfaces. The design drawings specify an allowable machining error range for the dimensions of each mating surface, i.e., the design tolerance, which translates into various degrees of tightness that may occur during actual assembly, i.e., the mating state.

[0089] Taking the radial mating surface as an example, assuming the design size of the turbine disk's outer diameter is 200mm and the design tolerance is +0.03 / -0.01, then its upper, middle, and lower tolerances are 200.03mm, 200.00mm, and 199.99mm, respectively. The design size of the baffle's inner diameter is 200mm and the design tolerance is +0.01 / -0.02, then its upper, middle, and lower tolerances are 200.01mm, 200.00mm, and 199.98mm, respectively. The upper, middle, and lower differences in the outer diameter of the turbine disk and the inner diameter of the baffle can be combined to form various fit states: for example, when the outer diameter of the turbine disk is machined with an upper difference and the inner diameter of the baffle is machined with a lower difference, the turbine disk is 0.05mm larger than the baffle, forming an interference fit, which is the tightest fit; when both are machined with a middle difference, a transition fit is formed; when the outer diameter of the turbine disk is machined with a lower difference and the inner diameter of the baffle is machined with an upper difference, the turbine disk is 0.02mm smaller than the baffle, forming a clearance fit, which is the loosest fit.

[0090] The above method can determine various mating states of radial mating surfaces, and similarly, various mating states of axial mating surfaces can be determined, providing input for subsequent contact stress analysis considering the dispersion of mating clearances.

[0091] Step S5043: Calculate the contact stress of the equivalent model based on each mating state to obtain the contact stress of the key parts.

[0092] Specifically, each fit condition is input into the equivalent model for finite element contact stress calculation to obtain the contact stress of each key component under each fit condition, so as to evaluate the impact of different fit conditions on the stress level of each key component.

[0093] Step S5044: Determine the fit state corresponding to the maximum contact stress as the target fit state.

[0094] Specifically, the greater the contact stress, the more prone critical components are to fatigue crack initiation under cyclic loading, and the greater the adverse impact on component life. Therefore, by comparing all contact stresses calculated in the above steps, the fit state corresponding to the maximum value is determined as the target fit state for subsequent transient stress analysis and life assessment. This ensures that the fatigue life of the component can be assessed under the most unfavorable assembly conditions, avoiding deviations from reality due to the failure to consider extreme fit states.

[0095] Step S505: Obtain the transient full load of the turbine disk-baffle assembly, and perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude.

[0096] Specifically, step S505 includes: Step S5051: Obtain the transient full load. Based on the transient full load and the target fit state, perform stress analysis on the equivalent model and extract the peak stress and valley stress of each key part.

[0097] Specifically, the transient full load includes the engine's speed, temperature, and aerodynamic loads at every moment during a typical flight mission (such as a complete cycle consisting of start-up, acceleration, cruise, and deceleration), representing a complete time history. The transient full load, along with the target engagement state, is input into an equivalent model and applied to the established contact pair of the turbine disk-baffle assembly for transient contact finite element stress analysis. The finite element software performs a stress calculation at each time step, thereby obtaining the stress-time curves for each critical component, such as... Figure 6 As shown, the maximum stress value in the stress curve is the peak stress, and the minimum stress value is the valley stress. Compared with the traditional method of life assessment based solely on the steady-state design point, this embodiment of the invention introduces both transient full load and target engagement state, making the calculated contact force and stress between the turbine disk and the baffle more consistent with actual working conditions, thus effectively improving the accuracy of life assessment.

[0098] In step S5052, half of the difference between the peak stress and the valley stress is taken as the stress amplitude of the critical part.

[0099] Specifically, half the difference between the peak stress and the valley stress of each critical component is taken as the stress amplitude of that critical component to measure the degree of load fluctuation that the critical component experiences during a flight mission cycle.

[0100] Step S506: Evaluate the fatigue life of the turbine disk-baffle assembly based on the stress amplitude.

[0101] Specifically, step S506 includes: Step S5061: For each critical part, based on the material fatigue performance data, determine the number of second cycles corresponding to the stress amplitude of the critical part.

[0102] Specifically, the stress amplitude of each key component is substituted into the material fatigue performance data to obtain the corresponding number of second cycles.

[0103] Step S5062: Calculate the ratio of the second cycle number to the preset lifespan dispersion coefficient, and use it as the third cycle number for the critical part.

[0104] Specifically, considering the dispersion of material data and computational uncertainty, the ratio of the second cycle number to the preset life dispersion coefficient is calculated and used as the third cycle number for this critical component. The preset life dispersion coefficient can be determined based on the confidence and reliability of the material data. For example, when using median material fatigue performance data (reliability R=50%, confidence C=95%), the preset life dispersion coefficient is taken as 5; when using... When calculating material fatigue performance data (reliability R=99.87%, confidence level C=90%), the preset life dispersion factor is set to 2.

[0105] Step S5063: The minimum value among the third cycle counts of all critical components is taken as the fatigue life of the turbine disk-baffle assembly.

[0106] Specifically, failure of any critical component will lead to the failure of the entire assembly; therefore, the fatigue life of the assembly is determined by the critical component with the shortest lifespan. The minimum number of third cycles for all critical components is taken as the low-cycle fatigue life assessment result for the turbine disk-baffle assembly.

[0107] This invention simplifies the original model through stress analysis and then adjusts the number of feature parts to establish a cyclic symmetric model, effectively reducing the model size and improving computational efficiency and accuracy. By performing equivalent conversion on the cyclic symmetric model, its mechanical behavior is made essentially equivalent to the original model, ensuring the accuracy of subsequent stress analysis. By applying various mating states to the equivalent model for contact stress analysis, the radial and axial contact mating relationships between the turbine disk and the baffle can be fully simulated, allowing for the selection of the target mating state. Furthermore, by considering the actual load changes under transient time histories and combining this with the target mating state, stress analysis is accurately performed and stress amplitudes are extracted. Fatigue life is then assessed based on these stress amplitudes, improving the accuracy of life assessment, enhancing engine reliability and safety, and providing a basis for lightweight design and high reliability assurance of key aero-engine components.

[0108] This invention can fully simulate the radial and axial contact fit relationship between the turbine disk and the baffle, while taking into account the scale of the finite element model to improve calculation efficiency and accuracy, improve the accuracy of stress calculation in the local high stress area of ​​the baffle, and accurately perform stress analysis and life design of the gas turbine disk-baffle assembly based on transient load history and fit clearance dispersion.

[0109] This embodiment also provides a life assessment device for a turbine disk-baffle assembly, which is used to implement the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0110] This embodiment provides a life assessment device for a turbine disk-baffle assembly, such as... Figure 7 As shown, it includes: The simplification module 701 is used to perform stress analysis and simplification on the original model of the turbine disk-baffle assembly to obtain a simplified model.

[0111] Adjustment module 702 is used to adjust the number of feature parts in the simplified model and establish a cyclic symmetric model.

[0112] The equivalent conversion module 703 is used to perform equivalent conversion on the cyclic symmetric model to obtain an equivalent model with mechanical behavior equivalent to the original model.

[0113] The first analysis module 704 is used to perform contact stress analysis based on the fit between the turbine disk and the baffle in the equivalent model, and to screen the target fit state.

[0114] The second analysis module 705 is used to obtain the transient full load of the turbine disk-baffle assembly, and to perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude.

[0115] Evaluation module 706 is used to evaluate the fatigue life of the turbine disk-baffle assembly based on stress amplitude.

[0116] In some alternative implementations, the simplification module 701 includes: The acquisition unit is used to acquire the initial full load of the turbine disk-baffle assembly in a typical flight mission.

[0117] The first analysis unit is used to perform stress analysis on the original model based on the initial full load, and obtain the stress of multiple characteristic parts of the turbine disk-baffle assembly.

[0118] The first calculation unit is used to determine the first cycle number corresponding to the stress of each feature part based on material fatigue performance data.

[0119] A segmentation unit is used to divide multiple feature regions into critical and non-critical regions based on the first iteration number of each feature region.

[0120] Simplified units are used to simplify non-critical parts in the original model to obtain a simplified model.

[0121] In some alternative implementations, adjustment module 702 includes: The first determining unit is used to determine the range of the cyclic symmetric model based on the number of bolt holes in the simplified model.

[0122] The adjustment unit is used to adjust the number of tenons in the simplified model so that the number of tenons and bolt holes are in a multiple relationship.

[0123] The second determining unit is used to apply cyclic symmetric boundary conditions to the simplified model after adjusting the number of parameters, based on the range of the cyclic symmetric model, to obtain the cyclic symmetric model.

[0124] In some alternative implementations, the equivalent conversion module 703 includes: The second calculation unit is used to calculate the material density at the equivalent wheel rim and the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent calculation.

[0125] The third calculation unit is used to calculate the elastic modulus of the material at the equivalent rear rim based on the difference in radial deformation between the model before and after adjustment.

[0126] The update unit is used to update the corresponding parameters of the cyclic symmetric model based on the material density at the equivalent rear rim, the centrifugal load applied to the tenon tooth surface of the equivalent rear rim, and the elastic modulus of the material at the equivalent rear rim, so as to obtain the equivalent model.

[0127] In some alternative implementations, the material density at the equivalent rear rim is calculated using the following formula:

[0128] In the formula, This represents the material density at the equivalent rear rim. This represents the material density at the rim in the original model; This represents the volume of a single tenon in the original model; This represents the volume of a single tenon in a cyclically symmetric model. Represents the centroid radius of a single tenon in the original model; Represents the centroid radius of a single tenon in a cyclic symmetric model; This indicates the number of tenons and mortises in the original model; This indicates the number of tenons and slots in a cyclically symmetric model; The equivalent centrifugal load applied to the tenon tooth surface of the wheel rim tenon groove is calculated using the following formula:

[0129] In the formula, This represents the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent effect. This represents the centrifugal load applied to the tenon tooth surface of the rim groove in the original model.

[0130] In some alternative implementations, the third computing unit includes: The first sub-element is used to establish the first finite element model of the turbine disk based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon tooth surface of the rim tenon.

[0131] The second sub-unit is established to create a second finite element model of the turbine disk based on the number of tenons in the cyclic symmetric model, the material density at the equivalent wheel rim, and the centrifugal load applied to the tenon tooth surface of the wheel rim tenon.

[0132] The calculation sub-unit is used to input the elastic modulus of the material at the rim of the original model into the first finite element model and the second finite element model respectively, and perform finite element calculations to obtain the first average radial deformation and the second average radial deformation.

[0133] A sub-element is determined to calculate the ratio of the second average radial deformation to the first average radial deformation. The product of this ratio and the elastic modulus of the material at the rim of the original model is then used to determine the elastic modulus of the material at the equivalent rim.

[0134] In some alternative implementations, the first analysis module 704 includes: Create elements to establish the contact pairs between the turbine disk and the baffle in the equivalent model.

[0135] The third determining unit is used to determine various mating states between the turbine disk and the baffle based on the design tolerances of the turbine disk and the baffle.

[0136] The fourth calculation unit is used to calculate the contact stress of the equivalent model based on each mating state, and to obtain the contact stress of the key parts.

[0137] The fourth determining unit is used to determine the fit state corresponding to the maximum contact stress as the target fit state.

[0138] In some alternative implementations, the second analysis module 705 includes: The second analysis unit is used to obtain the transient full load. Based on the transient full load and the target fit state, stress analysis is performed on the equivalent model to extract the peak stress and valley stress of each key part.

[0139] The fifth determining unit is used to take half of the difference between the peak stress and the valley stress as the stress amplitude of the critical part.

[0140] In some alternative implementations, the evaluation module 706 includes: The sixth determining unit is used to determine the second cycle number corresponding to the stress amplitude of each critical part based on material fatigue performance data.

[0141] The fifth calculation unit is used to calculate the ratio of the second cycle number to the preset lifespan dispersion coefficient, which serves as the third cycle number for critical parts.

[0142] The seventh determining unit is used to determine the minimum value among the third cycle counts of all key components as the fatigue life of the turbine disk-baffle assembly.

[0143] The turbine disk-baffle assembly life assessment device provided in this embodiment of the invention can execute the turbine disk-baffle assembly life assessment method provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects for executing the method. Further functional descriptions of the various modules and units described above are the same as in the corresponding embodiments described above, and will not be repeated here.

[0144] Figure 8 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention.

[0145] The following is a detailed reference. Figure 8 This diagram illustrates a suitable structural schematic for implementing an electronic device according to embodiments of the present invention. The electronic device may include a processor (e.g., a central processing unit, graphics processor, etc.) 801, which can perform various appropriate actions and processes based on a program stored in read-only memory (ROM) 802 or a program loaded from memory 808 into random access memory (RAM) 803. The RAM 803 also stores various programs and data required for the operation of the electronic device. The processor 801, ROM 802, and RAM 803 are interconnected via a bus 804. An input / output (I / O) interface 805 is also connected to the bus 804.

[0146] Typically, the following devices can be connected to I / O interface 805: input devices 806 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 807 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; memory devices 808 including, for example, magnetic tapes, hard disks, etc.; and communication devices 809. Communication device 809 allows electronic devices to communicate wirelessly or wiredly with other devices to exchange data. Although Figure 8 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown, and more or fewer devices may be implemented or have instead.

[0147] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 809, or installed from a memory 808, or installed from a ROM 802. When the computer program is executed by the processor 801, it performs the functions defined in the turbine disk-baffle assembly life assessment method of the embodiments of the present invention.

[0148] Figure 8 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0149] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code. When the software or computer code is accessed and executed by the computer, processor, or hardware, the life assessment method for the turbine disk-baffle assembly shown in the above embodiments is implemented.

[0150] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A method for assessing the lifespan of a turbine disk-baffle assembly, characterized in that, The method includes: The original model of the turbine disk-baffle assembly was subjected to stress analysis and simplified to obtain a simplified model; Adjust the number of feature parts in the simplified model to establish a cyclic symmetric model; The cyclic symmetric model is transformed into an equivalent model with mechanical behavior equivalent to the original model. Contact stress analysis is performed based on the fit state between the turbine disk and the baffle in the equivalent model to screen the target fit state; Obtain the transient full load of the turbine disk-baffle assembly, and perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude; The fatigue life of the turbine disk-baffle assembly is evaluated based on the stress amplitude. The step of adjusting the number of feature parts in the simplified model to establish a cyclic symmetric model includes: The range of the cyclic symmetric model is determined based on the number of bolt holes in the simplified model; Adjust the number of tenons in the simplified model so that the number of tenons and the number of bolt holes are in a multiple relationship; Based on the range of the cyclic symmetric model, cyclic symmetric boundary conditions are applied to the simplified model after adjusting the number of parameters to obtain the cyclic symmetric model. The equivalent transformation of the cyclic symmetric model to obtain an equivalent model with mechanical behavior equivalent to the original model includes: Calculate the equivalent material density at the rim and the equivalent centrifugal load applied at the tenon tooth surface of the rim tenon groove; Based on the difference in radial deformation before and after the adjustment, the elastic modulus of the material at the equivalent rear rim is calculated; Based on the equivalent rear rim material density, the equivalent centrifugal load applied to the rim tenon tooth surface, and the equivalent rear rim material elastic modulus, the corresponding parameters of the cyclic symmetric model are updated to obtain the equivalent model. The calculation of the elastic modulus of the material at the equivalent rear rim based on the difference in radial deformation before and after model adjustment includes: Based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon tooth surface of the rim tenon, a first finite element model of the turbine disk is established. Based on the number of tenons in the cyclic symmetric model, the material density at the equivalent wheel rim, and the centrifugal load applied at the tenon tooth surface of the wheel rim tenon after the equivalent process, a second finite element model of the turbine disk is established. The elastic modulus of the material at the rim of the original model is input into the first finite element model and the second finite element model respectively, and finite element calculation is performed to obtain the first average radial deformation and the second average radial deformation. Calculate the ratio of the second average radial deformation to the first average radial deformation, and multiply the ratio by the elastic modulus of the material at the rim of the original model to determine the elastic modulus of the material at the equivalent rim. The contact stress analysis based on the fit between the turbine disk and the baffle in the equivalent model, and the selection of target fit states, includes: Establishing a contact pair between the turbine disk and the baffle in the equivalent model includes: establishing contact pairs at the radial cylindrical positioning surface and the axial bolt connection surface in the equivalent model according to the actual assembly relationship between the turbine disk and the baffle; Based on the design tolerances of the turbine disk and the baffle, various mating states between the turbine disk and the baffle are determined. Contact stress is calculated for the equivalent model based on each mating state to obtain the contact stress at key locations. The fit state corresponding to the maximum contact stress is determined as the target fit state.

2. The method according to claim 1, characterized in that, The original model of the turbine disk-baffle assembly was subjected to stress analysis and simplification to obtain a simplified model, including: Obtain the initial full load of the turbine disk-baffle assembly in a typical flight mission; Stress analysis was performed on the original model based on the initial full load to obtain the stress at multiple characteristic parts of the turbine disk-baffle assembly; For each feature location, based on material fatigue performance data, the number of first cycles corresponding to the stress at the feature location is determined; Based on the first cycle count of each feature region, the multiple feature regions are divided into critical regions and non-critical regions; The simplified model is obtained by simplifying non-critical parts in the original model.

3. The method according to claim 1, characterized in that, The equivalent material density at the rear rim is calculated using the following formula: In the formula, This represents the material density at the equivalent rear rim. This represents the material density at the rim in the original model; This represents the volume of a single tenon in the original model; This represents the volume of a single tenon in a cyclically symmetric model. Represents the centroid radius of a single tenon in the original model; Represents the centroid radius of a single tenon in a cyclic symmetric model; This indicates the number of tenons and mortises in the original model; This indicates the number of tenons and slots in a cyclically symmetric model; The equivalent centrifugal load applied to the tenon tooth surface of the wheel rim tenon groove is calculated using the following formula: In the formula, This represents the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent effect. This represents the centrifugal load applied to the tenon tooth surface of the rim groove in the original model.

4. The method according to claim 2, characterized in that, The process of obtaining the transient full load of the turbine disk-baffle assembly, performing stress analysis on the equivalent model in conjunction with the target fit state, and extracting the stress amplitude includes: The transient full load is obtained, and stress analysis is performed on the equivalent model based on the transient full load and the target engagement state to extract the peak stress and valley stress of each key part. Half of the difference between the peak stress and the valley stress is taken as the stress amplitude of the critical part.

5. The method according to claim 4, characterized in that, The assessment of the fatigue life of the turbine disk-baffle assembly based on the stress amplitude includes: For each critical component, based on the material fatigue performance data, the number of second cycles corresponding to the stress amplitude of the critical component is determined; Calculate the ratio of the second cycle number to the preset lifetime dispersion coefficient, and use it as the third cycle number for the critical part; The minimum number of the third cycle counts for all critical components is taken as the fatigue life of the turbine disk-baffle assembly.

6. A life assessment device for a turbine disk-baffle assembly, characterized in that, The device includes: The simplification module is used to perform stress analysis and simplify the original model of the turbine disk-baffle assembly to obtain a simplified model; An adjustment module is used to adjust the number of feature parts in the simplified model and establish a cyclic symmetric model. An equivalent conversion module is used to perform equivalent conversion on the cyclic symmetric model to obtain an equivalent model whose mechanical behavior is equivalent to that of the original model. The first analysis module is used to perform contact stress analysis based on the fit state between the turbine disk and the baffle in the equivalent model, and to screen the target fit state. The second analysis module is used to obtain the transient full load of the turbine disk-baffle assembly, and perform stress analysis on the equivalent model in combination with the target fit state to extract the stress amplitude; An evaluation module is used to evaluate the fatigue life of the turbine disk-baffle assembly based on the stress amplitude; The adjustment module includes: The first determining unit is used to determine the range of the cyclic symmetric model based on the number of bolt holes in the simplified model; An adjustment unit is used to adjust the number of tenons in the simplified model so that the number of tenons and the number of bolt holes satisfy a multiple relationship. The second determining unit is used to apply cyclic symmetric boundary conditions to the simplified model after adjusting the number of parameters based on the range of the cyclic symmetric model, so as to obtain the cyclic symmetric model. The equivalent conversion module includes: The second calculation unit is used to calculate the material density at the equivalent wheel rim and the centrifugal load applied to the tenon tooth surface of the wheel rim tenon after the equivalent calculation. The third calculation unit is used to calculate the elastic modulus of the material at the equivalent rear rim based on the difference in radial deformation between the model before and after adjustment. The update unit is used to update the corresponding parameters of the cyclic symmetric model based on the material density at the equivalent rear rim, the centrifugal load applied to the tenon tooth surface of the equivalent rear rim, and the elastic modulus of the material at the equivalent rear rim, so as to obtain the equivalent model. The third computing unit includes: The first sub-unit is used to establish the first finite element model of the turbine disk based on the number of tenons in the original model, the material density at the rim, and the centrifugal load applied to the tenon tooth surface of the rim tenon. The second sub-unit is used to establish the second finite element model of the turbine disk based on the number of tenons in the cyclic symmetric model, the material density at the equivalent rear rim, and the centrifugal load applied at the tenon tooth surface of the equivalent rear rim tenon. The calculation subunit is used to input the elastic modulus of the material at the rim of the original model into the first finite element model and the second finite element model respectively, perform finite element calculations, and obtain the first average radial deformation and the second average radial deformation. A sub-unit is determined to calculate the ratio of the second average radial deformation to the first average radial deformation. The product of the ratio and the elastic modulus of the material at the rim of the original model is determined as the elastic modulus of the material at the equivalent rim. The first analysis module includes: A unit is established to establish a contact pair between the turbine disk and the baffle in the equivalent model, including: establishing contact pairs at the radial cylindrical positioning surface and the axial bolt connection surface in the equivalent model according to the actual assembly relationship between the turbine disk and the baffle; The third determining unit is used to determine various mating states between the turbine disk and the baffle based on the design tolerances of the turbine disk and the baffle. The fourth calculation unit is used to calculate the contact stress of the equivalent model based on each mating state to obtain the contact stress of the key parts. The fourth determining unit is used to determine the fit state corresponding to the maximum contact stress as the target fit state.

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